Airworthiness Directives; Raytheon Model Hawker 800XP and Hawker 800 (U-125A) Series Airplanes

[Federal Register Volume 65, Number 220 (Tuesday, November 14, 2000)]
[Rules and Regulations]
[Pages 68069-68071]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-28479]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-46-AD; Amendment 39-11970; AD 2000-22-22]
RIN 2120-AA64


Airworthiness Directives; Raytheon Model Hawker 800XP and Hawker 
800 (U-125A) Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Raytheon Model Hawker 800XP and Hawker 800 (U-
125A) series airplanes, that requires inspection of the wire bundle to 
relay ``KT'' on panel ``JA'' for correct routing, adequate clearance 
from the fuel cross-feed valve operating lever, and the presence of 
chafing; this amendment also requires corrective action, if necessary. 
The actions specified by this AD are intended to detect and correct 
chafing of the wire bundle exiting panel ``JA'' due to insufficient 
clearance from the fuel cross-feed valve operating lever. Such chafing 
of the wire bundle could result in a fire in the area of the fuel 
system in a confined space. This action is intended to address the 
identified unsafe condition.

DATES: Effective December 19, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 19, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Raytheon Aircraft Company, 9709 East Central, Wichita, 
Kansas 67206. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer, 
Systems and Propulsion Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4139; fax (316) 
946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Model Hawker 800XP and 
Hawker 800 (U-125A) series airplanes was published in the Federal 
Register on August 8, 2000 (65 FR 48404). That action proposed to 
require inspection of the wire bundle to relay ``KT'' on panel ``JA'' 
for correct routing, adequate clearance from the fuel cross-feed valve 
operating lever, and the presence of chafing. That action also proposed 
to require corrective action, if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

[[Page 68070]]

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 148 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 60 airplanes of U.S. registry 
will be affected by this required AD, that it will take approximately 1 
work hour per airplane to accomplish the required inspection, and that 
the average labor rate is $60 per work hour. Based on these figures, 
the cost impact of the inspection required by this AD on U.S. operators 
is estimated to be $3,600, or $60 per airplane.
    No estimate is provided for the cost impact of repairing the wire 
bundle or modifying the routing of the wire bundle or ensuring adequate 
clearance between the wire bundle and the fuel cross-feed valve 
operating lever because these costs will depend on the extent of the 
repairs or modifications required.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-22-22  Raytheon Aircraft Company: Amendment 39-11970. Docket 
2000-NM-46-AD.

    Applicability: Model Hawker 800XP series airplanes, as listed in 
Raytheon Service Bulletin SB 24-3212, dated August 1999; and Hawker 
800 (U-125A) series airplanes, as listed in Raytheon Service 
Bulletin SB 24-3213, dated February 2000; certificated in any 
category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (d) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct chafing of the wire bundle exiting panel 
``JA'' due to insufficient clearance from the fuel cross-feed valve 
operating lever, which could result in a fire in the area of the 
fuel system in a confined space, accomplish the following:

Inspection and Corrective Actions

    (a) Within 50 flight hours or 6 months after the effective date 
of this AD, whichever comes first, conduct a one-time detailed 
visual inspection of the panel ``JA'' wire bundle in accordance with 
the Accomplishment Instructions of Raytheon Aircraft Service 
Bulletin SB 24-3212, dated August 1999 (for Model 800XP series 
airplanes); or SB 24-3213, Revision 1, dated February 2000 (for 
Model 800 (U-125A) series airplanes; as applicable.
    (1) Ensure that the wire bundle is routed correctly, in 
accordance with Figure 1 of the applicable service bulletin.
    (2) Ensure that a minimum clearance of 0.25-inch exists between 
the wire bundle from relay ``KT'' and the fuel cross-feed valve 
operating lever throughout its range of travel.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (b) If the wire bundle is routed correctly and sufficient 
clearance exists, no further action is required by this AD.
    (c) If the wire bundle is not routed correctly or if sufficient 
clearance does not exist, prior to further flight, perform a 
detailed visual inspection of the wire bundle to relay ``KT'' for 
chafing, in accordance with the Accomplishment Instructions of 
Raytheon Aircraft Service Bulletin SB 24-3212, dated August 1999 
(for Model 800XP series airplanes); or SB 24-3213, Revision 1, dated 
February 2000 (for Model 800 (U-125A) series airplanes); as 
applicable.
    (1) If no chafing is detected, prior to further flight, ensure 
that the wire bundle is routed correctly and ensure that a minimum 
clearance of 0.25-inch exists between the wire bundle and the fuel 
cross-feed valve operating valve throughout its range of travel, in 
accordance with the applicable service bulletin.
    (2) If any chafing is detected, prior to further flight, repair 
the chafed wire, ensure that the wire bundle is routed correctly and 
ensure that a minimum clearance of 0.25-inch exists between the wire 
bundle and the fuel cross-feed valve operating valve throughout its 
range of travel, in accordance with the applicable service bulletin.

Alternative Methods of Compliance

    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Wichita Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Wichita ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Wichita ACO.

Special Flight Permits

    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to

[[Page 68071]]

a location where the requirements of this AD can be accomplished.

Incorporation by Reference

    (f) The actions shall be done in accordance with Raytheon 
Aircraft Service Bulletin SB 24-3212, dated August 1999; or Raytheon 
Aircraft Service Bulletin SB 24-3213, Revision 1, dated February 
2000; as applicable. This incorporation by reference was approved by 
the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained from Raytheon 
Aircraft Company, 9709 East Central, Wichita, Kansas 67206. Copies 
may be inspected at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita 
Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-
Continent Airport, Wichita, Kansas; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on December 19, 2000.

    Issued in Renton, Washington, on November 1, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-28479 Filed 11-13-00; 8:45 am]
BILLING CODE 4910-13-P

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